| タイトル | Electric propulsion for near-Earth space missions |
| 本文（外部サイト） | http://hdl.handle.net/2060/19800007836 |
| 著者（英） | Smith, W. W.; Terwilliger, C. H. |
| 著者所属（英） | Boeing Aerospace Co. |
| 発行日 | 1980-01-01 |
| 言語 | eng |
| 内容記述 | A set of missions was postulated that was considered to be representative of those likely to be desirable/feasible over the next three decades. The characteristics of these missions, and their payloads, that most impact the choice/design of the requisite propulsion system were determined. A system-level model of the near-Earth transportation process was constructed, which incorporated these mission/system characteristics, as well as the fundamental parameters describing the technology/performance of an ion bombardment based electric propulsion system. The model was used for sensitivity studies to determine the interactions between the technology descriptors and program costs, and to establish the most cost-effective directions for technology advancement. The most important factor was seen to be the costs associated with the duration of the mission, and this in turn makes the development of advanced electric propulsion systems having moderate to high efficiencies ( 50 percent) at intermediate ranges of specific impulse (approximately 1000 seconds) very desirable. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 80N16096
D180-25475-1
NASA-CR-159735 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/173545 |
